This paper proposes the use of curvilinear stiffeners as a mechanism to control supersonic panel flutter. To account for transverse shear deformation, the plate and stiffeners are modeled according to the First Order Shear Deformation Theory (FSDT) and Timoshenko Beam Theory, respectively. The Chebyshev Polynomials are the bases of the deflection and rotation functions in the Ritz Method. The aeroelastic load is formulated according to the first-order high Mach number approximation to potential flow theory. The Minimum Potential Energy and Hamilton's Principle are used to solve the problem. Vg and V_ω plots are used to determine the critical aerodynamic pressure and hence, to predict flutter of various unstiffened and stiffened, isotropic and composite plates. The results for the flutter of unstiffened and straight-stiffened plates have been validated through the comparison with published papers and the finite element software ANSYS~®. Several numerical examples are discussed, for which parametric studies for stiffener's shape variable and fiber orientation are performed. The flutter mode shapes are also presented. The present study attests that the critical dynamic pressure can be enhanced, and flutter successfully suppressed by changing the stiffener's path and fiber orientation.
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